FR3091901B1 - Noise reduction device with a honeycomb structure with oblique drilling - Google Patents
Noise reduction device with a honeycomb structure with oblique drilling Download PDFInfo
- Publication number
- FR3091901B1 FR3091901B1 FR1900548A FR1900548A FR3091901B1 FR 3091901 B1 FR3091901 B1 FR 3091901B1 FR 1900548 A FR1900548 A FR 1900548A FR 1900548 A FR1900548 A FR 1900548A FR 3091901 B1 FR3091901 B1 FR 3091901B1
- Authority
- FR
- France
- Prior art keywords
- noise reduction
- honeycomb structure
- reduction device
- layers
- oblique drilling
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000005553 drilling Methods 0.000 title 1
- 238000005192 partition Methods 0.000 abstract 2
- 230000001154 acute effect Effects 0.000 abstract 1
- 239000002131 composite material Substances 0.000 abstract 1
- 239000003190 viscoelastic substance Substances 0.000 abstract 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/045—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
- F02K1/82—Jet pipe walls, e.g. liners
- F02K1/827—Sound absorbing structures or liners
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/20—Three-dimensional
- F05D2250/28—Three-dimensional patterned
- F05D2250/283—Three-dimensional patterned honeycomb
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/30—Arrangement of components
- F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
- F05D2250/314—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being inclined in relation to each other
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/96—Preventing, counteracting or reducing vibration or noise
- F05D2260/963—Preventing, counteracting or reducing vibration or noise by Helmholtz resonators
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Abstract
L’invention concerne un dispositif (18) de réduction de bruit pour une turbomachine d’aéronef, ce dispositif présentant une structure en empilement de couches (20, 22, 24), de manière à ce qu’une première et une seconde peaux (22, 24) en matériau composite forment une première et une seconde couches extérieures (22, 24), ces couches extérieures (22, 24) étant sensiblement parallèles entre elles et enserrant une couche centrale (20). Cette couche centrale (20) présente une structure en nid d’abeille comportant des cloisons (26) s’étendant transversalement de la première couche extérieure (22) vers la seconde couche extérieure (24), de manière à former des cavités (28). Les cloisons (26) sont réalisée en matériau viscoélastique, et forment, avec les première et seconde couches extérieures (22, 24), un angle d’inclinaison aigu (α). Figure pour l'abrégé : figure 4The invention relates to a noise reduction device (18) for an aircraft turbine engine, this device having a stacked structure of layers (20, 22, 24), so that a first and a second skin ( 22, 24) made of composite material form a first and a second outer layers (22, 24), these outer layers (22, 24) being substantially parallel to each other and enclosing a central layer (20). This central layer (20) has a honeycomb structure comprising partitions (26) extending transversely from the first outer layer (22) towards the second outer layer (24), so as to form cavities (28) . The partitions (26) are made of viscoelastic material, and form, with the first and second outer layers (22, 24), an acute angle of inclination (α). Figure for abstract: Figure 4
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1900548A FR3091901B1 (en) | 2019-01-22 | 2019-01-22 | Noise reduction device with a honeycomb structure with oblique drilling |
CN202080013823.1A CN113423934A (en) | 2019-01-22 | 2020-01-22 | Noise reduction device with obliquely pierced honeycomb structure |
EP20705427.1A EP3914820B1 (en) | 2019-01-22 | 2020-01-22 | Noise reducing device having an obliquely pierced honeycomb structure |
PCT/FR2020/050078 WO2020152418A1 (en) | 2019-01-22 | 2020-01-22 | Noise reducing device having an obliquely pierced honeycomb structure |
US17/423,633 US20220099022A1 (en) | 2019-01-22 | 2020-01-22 | Noise reducing device having an obliquely pierced honeycomb structure |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1900548 | 2019-01-22 | ||
FR1900548A FR3091901B1 (en) | 2019-01-22 | 2019-01-22 | Noise reduction device with a honeycomb structure with oblique drilling |
Publications (2)
Publication Number | Publication Date |
---|---|
FR3091901A1 FR3091901A1 (en) | 2020-07-24 |
FR3091901B1 true FR3091901B1 (en) | 2020-12-25 |
Family
ID=67742504
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
FR1900548A Active FR3091901B1 (en) | 2019-01-22 | 2019-01-22 | Noise reduction device with a honeycomb structure with oblique drilling |
Country Status (5)
Country | Link |
---|---|
US (1) | US20220099022A1 (en) |
EP (1) | EP3914820B1 (en) |
CN (1) | CN113423934A (en) |
FR (1) | FR3091901B1 (en) |
WO (1) | WO2020152418A1 (en) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3126334B1 (en) * | 2021-08-30 | 2023-07-21 | Safran Nacelles | Process for manufacturing an acoustic panel with oblique cavities |
Family Cites Families (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3850261A (en) * | 1973-03-01 | 1974-11-26 | Gen Electric | Wide band width single layer sound suppressing panel |
US5706651A (en) * | 1995-08-29 | 1998-01-13 | Burbank Aeronautical Corporation Ii | Turbofan engine with reduced noise |
KR100628850B1 (en) * | 2004-11-03 | 2006-09-26 | 박기호 | A method of producing curved honeycomb structural |
FR2928415B1 (en) * | 2008-03-07 | 2010-12-03 | Aircelle Sa | ACOUSTIC PANEL OF A NACELLE OF AN AIRCRAFT |
FR2938014B1 (en) * | 2008-11-06 | 2011-04-15 | Aircelle Sa | ACOUSTICAL ATTENUATION PANEL FOR AN AIRCRAFT ENGINE NACELLE |
CN102301122B (en) * | 2008-07-30 | 2014-05-14 | 埃尔塞乐公司 | Acoustic attenuation panel for aircraft engine nacelle |
WO2010089496A1 (en) * | 2009-02-03 | 2010-08-12 | Airbus Operations Sas | Acoustic processing panel, more particularly adapted for an air intake in an aircraft nacelle |
FR2984280B1 (en) * | 2011-12-15 | 2013-12-20 | Aircelle Sa | AIR INTAKE STRUCTURE FOR TURBOREACTOR NACELLE |
US10184398B2 (en) * | 2013-10-17 | 2019-01-22 | Rohr, Inc. | Acoustic structural panel with slanted core |
US10156243B2 (en) * | 2015-05-04 | 2018-12-18 | Safran Aero Boosters Sa | Composite splitter lip for axial turbomachine compressor |
FR3051019B1 (en) * | 2016-05-03 | 2020-01-10 | Airbus Operations | STRUCTURE PROVIDING ACOUSTIC WAVE ATTENUATION AND HEAT EXCHANGE |
US11498306B2 (en) * | 2017-06-07 | 2022-11-15 | Ihi Corporation | Sound-absorbing panel and manufacturing method for same |
US10577117B2 (en) * | 2017-08-04 | 2020-03-03 | Hexcel Corporation | Angled acoustic honeycomb |
-
2019
- 2019-01-22 FR FR1900548A patent/FR3091901B1/en active Active
-
2020
- 2020-01-22 EP EP20705427.1A patent/EP3914820B1/en active Active
- 2020-01-22 US US17/423,633 patent/US20220099022A1/en active Pending
- 2020-01-22 WO PCT/FR2020/050078 patent/WO2020152418A1/en unknown
- 2020-01-22 CN CN202080013823.1A patent/CN113423934A/en active Pending
Also Published As
Publication number | Publication date |
---|---|
FR3091901A1 (en) | 2020-07-24 |
US20220099022A1 (en) | 2022-03-31 |
EP3914820B1 (en) | 2024-02-28 |
CN113423934A (en) | 2021-09-21 |
WO2020152418A1 (en) | 2020-07-30 |
EP3914820A1 (en) | 2021-12-01 |
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Legal Events
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PLFP | Fee payment |
Year of fee payment: 2 |
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PLSC | Publication of the preliminary search report |
Effective date: 20200724 |
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PLFP | Fee payment |
Year of fee payment: 3 |
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PLFP | Fee payment |
Year of fee payment: 4 |
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PLFP | Fee payment |
Year of fee payment: 5 |
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PLFP | Fee payment |
Year of fee payment: 6 |